Patent Application
20250108933
This application claims the benefit of India Provisional Application No. 202311065719 filed Sep. 29, 2023, the disclosure of which is incorporated herein by reference in its entirety.
The present disclosure relates to ram air turbine systems, and in particular to stowing of the ram air turbine in the fuselage of an aircraft after previous deployment of the ram air turbine.
In general, ram air turbine (“RAT”) systems are aircraft emergency power systems used to provide emergency electrical and/or hydraulic power to aircraft in the case of loss of both primary and secondary power sources for the aircraft. System operation can require the RAT to transition from a stowed position internal to the aircraft fuselage to a deployed position external to the aircraft fuselage. The RAT may deploy automatically in an engine failure event, or when commanded by the aircraft flight crew. Additionally, the RAT may be deployed on the ground when the system is periodically tested by maintenance personnel. The RAT typically deploys vis a spring-loaded lever and cannot be returned to the stowed position during aircraft flight. A stow mechanism is located in the fuselage and is connected to the RAT, and is activated by a switch mechanism mounted in the fuselage.
In one exemplary embodiment, a ram air turbine system of an aircraft includes a ram air turbine selectably movable between a stowed position and an extended position at an aircraft, and a retraction mechanism operably connected to the ram air turbine and configured to selectably move the ram air turbine from the extended position toward the stowed position. A stow panel is separate from the aircraft and is selectably connectible to the retraction mechanism. The stow panel is configured to signal the retraction mechanism to initiate movement of the ram air turbine from the extended position.
Additionally or alternatively, in this or other embodiments the system includes a stow connector through which the stow panel is selectably connectible to the retraction mechanism. The stow connector includes an aircraft connector portion positioned at the aircraft, and a panel connector portion positioned at the stow panel and operably connectible to the aircraft connector portion.
Additionally or alternatively, in this or other embodiments the aircraft connector portion is operably connected to the retraction mechanism via a retraction lead.
Additionally or alternatively, in this or other embodiments the aircraft connector portion is located at one of an exterior surface of an aircraft fuselage or a fuselage pocket of the aircraft fuselage.
Additionally or alternatively, in this or other embodiments a connector cover is removably positioned over the aircraft connector portion.
Additionally or alternatively, in this or other embodiments the connector cover is attached to an aircraft structure using one of a cable, a string or a strap.
Additionally or alternatively, in this or other embodiments the signal is one of an electrical signal, an optical signal, or a hydraulic signal.
Additionally or alternatively, in this or other embodiments the stow panel includes at least a signal transmitter, and a switch operably connected to the signal transmitter such that when the switch is activated the signal transmitter transmits the signal.
Additionally or alternatively, in this or other embodiments the stow panel further includes a power source operably connected to the switch and the signal transmitter.
Additionally or alternatively, in this or other embodiments the ram air turbine is configured to be moved from the extended position to the stowed position.
In another exemplary embodiment, an aircraft includes an aircraft fuselage, a ram air turbine assembly located at the aircraft fuselage and selectably movable between a stowed position and an extended position, and a retraction mechanism operably connected to the ram air turbine and configured to selectably move the ram air turbine from the extended position toward the stowed position. An aircraft connector portion is located at the aircraft fuselage and is configured to be selectably connectible to a stow panel separate from the aircraft.
Additionally or alternatively, in this or other embodiments the aircraft connector portion is operably connected to the retraction mechanism via a retraction lead.
Additionally or alternatively, in this or other embodiments the aircraft connector portion is positioned at one or an exterior surface of an aircraft fuselage or a fuselage pocket of the aircraft fuselage.
Additionally or alternatively, in this or other embodiments the retraction mechanism is configured to receive a signal from the stow panel via the aircraft connector portion to initiate movement of the ram air turbine from the extended position.
Additionally or alternatively, in this or other embodiments the signal is one of an electrical signal, an optical signal, or a hydraulic signal.
Additionally or alternatively, in this or other embodiments a connector cover is removably positioned over the aircraft connector portion.
Additionally or alternatively, in this or other embodiments the connector cover is attached to an aircraft structure using one of a cable, a string or a strap.
In yet another exemplary embodiment, a method of operating a ram air turbine system of an aircraft includes connecting a stow panel separate from the aircraft to a retraction mechanism located at the aircraft and operably connected to the ram air turbine, transmitting a signal from the stow panel to the retraction mechanism via the connection, and initiating operation of the retraction mechanism in response to receiving the signal to retract the ram air turbine from the extended position toward the stowed position.
Additionally or alternatively, in this or other embodiments the stow panel is removed from connection with the retraction mechanism after the ram air turbine reaches the stowed position.
Additionally or alternatively, in this or other embodiments the signal is transmitted by activation of a switch at the stow panel.
The following descriptions should not be considered limiting in any way. With reference to the accompanying drawings, like elements are numbered alike:
A detailed description of one or more embodiments of the disclosed apparatus and method are presented herein by way of exemplification and not limitation with reference to the figures.
Referring now to
The RAT assembly 14 also includes a strut 30 connected at a first end 32 to the turbine 20 adjacent the lower gear box 28, and coupled at a second, opposite end 34 to a generator housing 36. The generator housing 36, and therefore the strut 30 and turbine 20, is supported on the aircraft structure and is configured to rotate about a pivot 38 to provide for movement of the RAT assembly 14 between the stowed position 16 and the deployed position 18. The generator housing 36 supports a generator (not shown) that is driven by the plurality of turbine blades 22. The example generator is disposed within the generator housing 36. The turbine blades 22 rotate in response to the airstream A along the outside of the aircraft structure 10 to drive the generator. As appreciated, although the example RAT assembly 14 is disclosed with a generator, the ram air turbine 20 could also drive any other device, such as a hydraulic pump for example. The RAT assembly 14 includes a release lever 40 configured to rotate about a pivot 38 attached to the generator housing 36.
Referring now to
Referring now to
Referring again to
The RAT stow panel 50 includes, in some embodiments, a power source 64, a signal transmitter 66 and a switch 68 contained in a panel housing 70. The switch 68 is connected to the power source 64 and the signal transmitter 66 such that when the switch 68 is activated the signal transmitter 66 transmits a stow signal along a panel lead 72 and through the stow connector 52 to the retraction mechanism 48 which then retracts or stows the RAT assembly 14 in the aircraft fuselage 46.
Referring now to
Utilizing the stand-alone RAT stow panel 50 which is not part of the aircraft 44 is advantageous for a number of reasons including the ability to share one or two such devices among several aircraft, thus saving cost of procurement of the RAT stow panels 50. Further, removing the RAT stow panel 50 from the aircraft 44 and storing the device on the ground saves weight on the aircraft 44. Additionally, the RAT stow panel 50 may be simpler and more cost effective since airworthiness of the device is not required, and since the RAT stow panel 50 is not part of an aircraft system, the required design, development and certification effort would be reduced.
While particular embodiments have been described, alternatives, modifications, variations, improvements, and substantial equivalents that are or may be presently unforeseen may arise to applicants or others skilled in the art. Accordingly, the appended claims as filed and as they may be amended are intended to embrace all such alternatives, modifications variations, improvements, and substantial equivalents.
The term “about” is intended to include the degree of error associated with measurement of the particular quantity based upon the equipment available at the time of filing the application.
The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the present disclosure. As used herein, the singular forms “a”, “an” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms “comprises” and/or “comprising,” when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, element components, and/or groups thereof.
While the present disclosure has been described with reference to an exemplary embodiment or embodiments, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the scope of the present disclosure. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the present disclosure without departing from the essential scope thereof. Therefore, it is intended that the present disclosure not be limited to the particular embodiment disclosed as the best mode contemplated for carrying out this present disclosure, but that the present disclosure will include all embodiments falling within the scope of the claims.
| Number | Date | Country | Kind |
|---|---|---|---|
| 202311065719 | Sep 2023 | IN | national |
